|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:Space_Launch_System
gptkb:space_mission
|
|
gptkbp:average_temperature
|
-253° C to 1,000° C
|
|
gptkbp:challenges
|
overcome during development
|
|
gptkbp:check_in_time
|
up to 1,000 seconds
|
|
gptkbp:collaboration
|
international space agencies
|
|
gptkbp:community_engagement
|
active outreach programs
|
|
gptkbp:control_system
|
digital control system
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut
|
multiple successful launches
|
|
gptkbp:design
|
15 years
|
|
gptkbp:development
|
NASA and ULA collaboration
|
|
gptkbp:development_cost
|
$100 million
|
|
gptkbp:diameter
|
1.1 meters
|
|
gptkbp:educational_programs
|
STEM initiatives
|
|
gptkbp:engine_configuration
|
single engine
|
|
gptkbp:engine_type
|
gptkb:Team_Rocket
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:exhaust_system
|
expander cycle
|
|
gptkbp:facilities
|
gptkb:NASA_Marshall_Space_Flight_Center
|
|
gptkbp:first_flight
|
gptkb:2016
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
liquid hydrogen and liquid oxygen
cryogenic tanks
|
|
gptkbp:future_prospects
|
promising for deep space exploration
|
|
gptkbp:gimbal_range
|
±5 degrees
|
|
gptkbp:has_documentation
|
available online
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RL10 C-3
|
|
gptkbp:ignition_system
|
gptkb:spark_plug
|
|
gptkbp:invention
|
multiple patents filed
|
|
gptkbp:launch_vehicle
|
gptkb:Atlas_V
|
|
gptkbp:length
|
4.5 meters
|
|
gptkbp:maintenance
|
5 years
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:mission
|
geostationary transfer orbit
|
|
gptkbp:number_of_rooms
|
1,000 psi
single chamber
|
|
gptkbp:operational_period
|
staged combustion
|
|
gptkbp:operational_use
|
interplanetary missions
|
|
gptkbp:part_of
|
gptkb:NASA's_Space_Launch_System
|
|
gptkbp:partnerships
|
with universities and research institutions
|
|
gptkbp:propulsion
|
18.6
22,300 lbf
|
|
gptkbp:public_interest
|
high
|
|
gptkbp:reliability
|
high
|
|
gptkbp:safety_record
|
excellent
|
|
gptkbp:specific_impulse
|
450 seconds
|
|
gptkbp:status
|
in service
|
|
gptkbp:upgrades
|
planned improvements
|
|
gptkbp:used_in
|
Centaur upper stage
|
|
gptkbp:user_countries
|
used by several countries
|
|
gptkbp:weight
|
1,200 kg
|
|
gptkbp:bfsParent
|
gptkb:RL10_rocket_engine
|
|
gptkbp:bfsLayer
|
6
|